三级轴流压气机复合沟槽式机匣处理扩稳研究  

Investigation on Flow Mechanisms of Stall Margin Improvement of Compound Slots Casing Treatment for a 3.5-Stage High-Speed Axial-Flow Compressor

作　　者：张夏雯 花雨 李聪 琚亚平[1] 张楚华[1] ZHANG Xiawen;HUA Yu;LI Cong;JU Yaping;ZHANG Chuhua(School of Energy and Power Engineering,Xi'an Jiaotong University,Xi'an 710049,China;AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]西安交通大学能源与动力工程学院,西安710049 [2]中国航空发动机集团有限公司沈阳发动机研究所,沈阳110015

出　　处：《工程热物理学报》2023年第10期2673-2684,共12页Journal of Engineering Thermophysics

基　　金：国家重大科技专项专题(No.2017-II-0006-0020);国家重点研发计划课题(No.2016YFB0200901);国家自然科学基金项目(No.51776154)。

摘　　要：机匣处理作为现代高负荷压气机解决裕度不足问题的重要手段,对保障燃机运行安全性及装置技术先进性具有重要影响。本文针对多级高速轴流压气机易出现低转速下裕度不足的问题,对某3.5级高速轴流压气机在新型复合沟槽式机匣处理下70%~100%设计转速范围内的四种转速进行了全三维定常数值模拟,结合低转速下光壁机匣的失稳特性重点分析了复合沟槽式机匣处理的扩稳流动机理。结果表明:复合沟槽式机匣处理显著提高了80%设计转速下的失速裕度,裕度提高了13.73%。扩稳机理为:后段槽内泄漏间歇性降低叶尖两侧压差,削弱叶顶间隙泄漏射流强度;叶顶间隙泄漏流、叶尖前缘泄漏涡以及叶片表面附面层被抽吸进入后段槽阻断旋绕从而抑制泄漏涡的形成;前段槽回流在一定范围内降低了第一级动叶进气冲角。研究工作对提高压气机性能调节技术水平具有重要指导价值。Casing treatment,as one of effective methods to widen stable operating range of modern high-loading compressors,is of great influence on the operation safety and technology advancement of gas turbine.To address the problem of insufficient stall margin at low speed conditions,threedimensional steady numerical simulations of a 3.5-stage high-speed axial-fow compressor with a new type of compound slots casing treatment at 70%~100%four design speeds are conducted.The fow mechanisms of stall margin improvements of new compound slots casing treatment are analyzed by comparing with the flow characteristics of instability for the investigated compressor with smooth casing.The results show that the compound slots casing treatment significantly improves the stall margin at 80%design speed by 13.73 percent.The stability expansion at 80%design speed is mainly attributed to three flow mechanisms,i.e.,the intermittent leakage of rear slots weakens the tip leakage jet flow by reducing the pressure differential between suction and pressure sides,the suction of tip clearance leakage fow,tip leakage vortex at leading edge and boundary layer of the blade by rear slots inhibits the formation of tip leakage vortex,the recirculation of front slots reduces the incidence angle of first rotor blade row.This work has practical significance for the improvement of performance regulation technology of multi-stage axial-fow compressor.

关 键 词：多级高速轴流压气机 机匣处理 扩稳调节 数值模拟 

分 类 号：TK474.8[动力工程及工程热物理—动力机械及工程]